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2018-02-08 BELL HELICOPTER TEXTRON:
Amendment 39-19161; Docket No. FAA-2017-0895; Product Identifier 2017-SW-048-AD.

(a) APPLICABILITY

    This AD applies to Bell Helicopter Textron (Bell) Model 204B, 205A and
    205A-1 helicopters  with  a  Helicopter Technology Company (HTC)  main
    rotor (M/R) blade part number 204P2100-101 installed,  certificated in
    any category.

(b) UNSAFE CONDITION

    This AD defines the unsafe condition as a crack in an M/R blade, which
    could result in failure of an M/R blade  and  subsequent loss of heli-
    copter control.

(c) EFFECTIVE DATE

    This AD becomes effective February 1, 2018.

(d) COMPLIANCE

    You are responsible  for performing each action required  by  this  AD
    within the specified compliance time unless it has already been accom-
    plished prior to that time.

(e) REQUIRED ACTIONS

(1) Within 25 hours time-in-service (TIS)  or  2 weeks,  whichever  occurs
    first,  and  thereafter  at  intervals not to exceed 25 hours TIS or 2
    weeks, whichever occurs first,  clean the upper and lower exposed sur-
    faces of each M/R blade from an area starting  at the butt end  of the
    blade to three inches outboard  of the doublers.  Using a 3X or higher
    power magnifying glass and a light, inspect as follows:

(i) Visually inspect the exposed areas of the lower grip pad and upper and
    lower grip plates of each M/R blade for a crack and any corrosion.

(ii) On the upper and lower exposed surfaces of each M/R blade  from blade
     stations 24.5 to 35 for the chord width,  visually inspect  each lay-
     ered doubler and blade skin for a crack and  any corrosion.  Pay par-
     ticular attention for any cracking in a doubler  or  skin near  or at
     the  same  blade station  as  the blade  retention  bolt hole  (blade
     station 28).

(iii) Visually inspect the exposed areas of each bond line at the edges of
      the lower grip pad,  upper and lower grip plates,  and  each layered
      doubler (bond lines)  on the upper  and  lower surfaces  of each M/R
      blade for the entire length  and  chord width for an edge void,  any
      corrosion, loose or damaged adhesive squeeze-out, and an edge delam-
      ination.  Pay particular attention to any crack  in the paint finish
      that follows the outline of a grip pad, grip plate,  or doubler, and
      to any loose  or  damaged adhesive squeeze-out,  as these may be the
      indication of an edge void.

(2) If there is a crack, any corrosion, an edge void, loose or damaged ad-
    hesive squeeze-out,  or  an edge delamination during any inspection in
    paragraph (e)(1) of this AD, before further flight, do the following:

(i) If there is a crack in a grip pad  or  any grip plate or doubler,  re-
    place the M/R blade with an airworthy M/R blade.

(ii) If there is a crack in the M/R blade skin  that is within maximum re-
     pair damage limits repair the M/R blade. If the crack exceeds maximum
     repair  damage  limits,  replace the M/R blade  with an airworthy M/R
     blade.

(iii) If there is any corrosion  within maximum repair damage limits,  re-
      pair the M/R blade.  If the corrosion  exceeds maximum repair damage
      limits, replace the M/R blade with an airworthy M/R blade.

(iv) If there is an edge void  in the grip pad  or  in  a  grip  plate  or
     doubler, determine the length and depth using a feeler gauge.  Repair
     the M/R blade if the edge void is within maximum repair damage limits
     or replace the M/R blade with an airworthy M/R blade.

(v) If there is an edge void in a grip plate or  doubler near the outboard
    tip,  tap inspect the affected area to determine the size and shape of
    the void.  Repair the M/R blade if the edge void is within maximum re-
    pair damage limits  or  replace  the  M/R blade  with an airworthy M/R
    blade.

(vi) If there is any loose  or  damaged adhesive squeeze-out  along any of
     the bond lines, trim or scrape away the adhesive without damaging the
     adjacent surfaces or parent material of the M/R blade.  Determine  if
     there is an edge void or any corrosion by lightly sanding the trimmed
     area smooth using 280  or finer grit paper.  If there is no edge void
     or corrosion, refinish the sanded area.

(vii) If there is an edge delamination  along any of the bond lines  or  a
      crack in the paint finish,  determine if there is an edge void  or a
      crack in the grip pad, grip plate, doubler or skin by removing paint
      from the affected area by lightly sanding  in  a  spanwise direction
      using 180-220 grit paper.  If there are no edge voids and no cracks,
      refinish the sanded area.

(viii) If any parent material is removed during any sanding or trimming in
       paragraphs (e)(2)(vi)  or (e)(2)(vii) of this AD,  repair  the  M/R
       blade if the damage is within maximum repair damage limits  or  re-
       place the M/R blade with an airworthy M/R blade.

(3) If there is a crack during any inspection  in paragraph (e)(1) of this
    AD, within 10 days after completing the inspection,  report the infor-
    mation requested in Appendix 1 to this AD  by mail  to the Los Angeles
    ACO Branch, Compliance and Airworthiness Division, FAA, 3960 Paramount
    Blvd., Lakewood, California 90712; attn. Galib Abumeri; or by email to
    galib.abumeri@faa.gov.

(f) SPECIAL FLIGHT PERMITS

    Special flight permits are prohibited.

(g) PAPERWORK REDUCTION ACT BURDEN STATEMENT

    A federal agency may not conduct or sponsor,  and  a person is not re-
    quired to respond to,  nor shall  a person be subject to a penalty for
    failure to comply with a collection of information  subject to the re-
    quirements of the Paperwork Reduction Act  unless  that  collection of
    information displays  a  current  valid  OMB Control Number.  The  OMB
    Control Number for this information collection  is  2120-0056.  Public
    reporting  for  this  collection  of  information  is  estimated to be
    approximately 30 minutes per response,  including the time for review-
    ing instructions,  completing and reviewing the collection of informa-
    tion.  All responses  to this collection of information are mandatory.
    Comments concerning the accuracy of this burden  and  suggestions  for
    reducing the burden should be directed to the FAA at: 800 Independence
    Ave. SW, Washington, DC 20591,  Attn: Information Collection Clearance
    Officer, AES-200.

(h) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, Los Angeles ACO Branch,  FAA,  may approve AMOCs for this
    AD.  Send  your  proposal  to:   Galib  Abumeri,   Aerospace  Engineer
    (Structures), Airframe Section, Los Angeles ACO Branch, Compliance and
    Airworthiness Division, FAA, 3960 Paramount Blvd, Lakewood, California
    90712; telephone 562-627-5324; email galib.abumeri@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate
    or  under 14 CFR part 91,  subpart K,  we suggest that you notify your
    principal inspector, or lacking a principal inspector,  the manager of
    the local flight standards district office or certificate holding dis-
    trict office before operating  any  aircraft complying  with  this  AD
    through an AMOC.

(i) ADDITIONAL INFORMATION

    HTC Service Notice No. 204-2100-1,  dated July 5, 2017;  Alert Service
    Bulletin (ASB) No. UH-1H-13-09,  dated January 14, 2013;  Bell ASB No.
    204-75-1  and  Bell ASB No. 205-75-5,  both  Revision C and both dated
    April 25, 1979,  which  are  not  incorporated  by  reference, contain
    additional information about the subject of this AD.  For  service in-
    formation identified in this AD, contact Bell Helicopter Textron, Inc.
    PO Box 482, Fort Worth, TX 76101;  telephone (817) 280-3391; fax (817)
    280-6466;  or  at  http://www.bellcustomer.com/files/.  You may review
    this service information  at the FAA,  Office of the Regional Counsel,
    Southwest Region,  10101 Hillwood Pkwy,  Room  6N-321,  Fort Worth, TX
    76177.

(j) SUBJECT

    Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor Blades.

Issued in Fort Worth, Texas,  on January 9, 2018.  James A. Grigg,  Acting
Director, Compliance & Airworthiness Division, Aircraft Certification Ser-
vice.

                         APPENDIX 1 TO AD 2018-02-08

Please report the following information by  mail  to  the  Los Angeles ACO
Branch, Compliance and Airworthiness Division,  FAA, 3960 Paramount Blvd.,
Lakewood, California 90712; attn. Galib Abumeri; or by email to galib.
abumeri@faa.gov.
    (1) Date of inspection:
    (2) Aircraft N-number:
    (3) M/R blade serial number:
    (4) M/R blade hours of time-in-service:
    (5) Location of each crack:
    (6) Dimension of each crack:
    (7) Primary operating location of the M/R blade:

FOR  FURTHER  INFORMATION  CONTACT:  Galib  Abumeri,   Aerospace  Engineer
(Structures),  Airframe  Section,  Los Angeles ACO Branch,  Compliance and
Airworthiness Division,  FAA,  3960 Paramount Blvd.,  Lakewood, California
90712; telephone 562-627-5324; email galib.abumeri@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0895; Product Identifier 2017-SW-048-AD; Amendment
39-19161; AD 2018-02-08]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for Bell
Helicopter Textron (Bell) Model 204B, 205A, and 205A-1 helicopters with
a Helicopter Technology Company (HTC) main rotor (M/R) blade installed.
This AD requires cleaning and visually inspecting the M/R blades, and
depending on the outcome of the inspection, repairing or replacing the
M/R blades. This AD is prompted by a report of an M/R blade with a
fatigue crack in the grip plate and doublers at the blade retention
bolt hole. The actions of this AD are intended to correct an unsafe
condition on these products.

DATES: This AD becomes effective February 1, 2018.
We must receive comments on this AD by March 19, 2018.

ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the
online instructions for sending your comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

You may examine the AD docket on the internet at http://www.regulations.
gov by searching for and locating Docket No. FAA-2017-
0895; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this AD, the economic evaluation, any comments received, and other
information. The street address for Docket Operations (telephone 800-
647-5527) is in the ADDRESSES section. Comments will be available in
the AD docket shortly after receipt.
For service information identified in this final rule, contact Bell
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone
(817) 280-3391; fax (817) 280-6466; or at http://www.bellcustomer.com/
files/. You may review the referenced service information at the FAA,
Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy,
Room 6N-321, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer
(Structures), Airframe Section, Los Angeles ACO Branch, Compliance and
Airworthiness Division, FAA, 3960 Paramount Blvd., Lakewood, California
90712; telephone 562-627-5324; email galib.abumeri@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments prior to it becoming effective. However, we
invite you to participate in this rulemaking by submitting written
comments, data, or views. We also invite comments relating to the
economic, environmental, energy, or federalism impacts that resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, explain the reason for any recommended change, and
include supporting data. To ensure the docket does not contain
duplicate comments, commenters should send only one copy of written
comments, or if comments are filed electronically, commenters should
submit them only one time. We will file in the docket all comments that
we receive, as well as a report summarizing each substantive public
contact with FAA personnel concerning this rulemaking during the
comment period. We will consider all the comments we receive and may
conduct additional rulemaking based on those comments.

Discussion

We are adopting a new AD for Bell 204B, 205A and 205A-1 helicopters
with an HTC M/R blade part number (P/N) 204P2100-101 installed. This AD
requires repetitive inspections of the exposed areas of the lower grip
pad and upper and lower grip plates of each M/R blade for a crack,
corrosion, an edge void, loose or damaged adhesive squeeze-out, and an
edge delamination.
The actions of this AD are the same as those required by AD 2016-
22-07 (81 FR 74285, October 26, 2016), which applies to Bell Model
204B, 205A and 205A-1 helicopters with an M/R blade P/N 204-011-200-001
or P/N 204-011-250-(all dash numbers) installed. AD 2016-22-07 was
prompted by a report of an M/R blade with multiple fatigue cracks
around the retention bolt hole.
This AD is prompted by a report that during a ground inspection, a
crack was discovered in the grip plate and doublers at the blade
retention bolt hole of a UH-1B helicopter model. The blade, which HTC
produced for restricted category and commercial model helicopters, had
926 hours TIS and is of the same design as the M/R blades in AD 2016-
22-07. We are issuing this AD to detect or prevent a crack, which could
lead to failure of an M/R blade and subsequent loss of helicopter
control.

FAA's Determination

We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.

Related Service Information

HTC has issued Service Notice No. 204-2100-1 on July 5, 2017, for
affected helicopters with M/R blade P/N 204P2100-101, serial numbers
A099 through A119 installed. This service notice specifies cleaning and
visually inspecting the M/R blades and depending on the outcome,
repairing or replacing the blades in accordance with AD 2016-23-09.
We also reviewed Bell Helicopter Alert Service Bulletin (ASB) No.
UH-1H-13-09, dated January 14, 2013, for the Model UH-1H helicopter.
ASB No. UH-1H-13-09 specifies a one-time visual inspection, within 10
hours time-in-service (TIS), of the lower grip pad and upper and lower
grip plates for cracks, edge voids, and loose or damaged adhesive
squeeze-out. ASB No. UH-1H-13-09 also specifies a repetitive and more
detailed visual inspection, daily and at every 150 hours TIS, of the
lower grip pad, upper and lower grip plates, and all upper and the
lower doublers for cracks, corrosion, edge voids, and loose or damaged
adhesive squeeze-out.
Lastly, we reviewed Bell Helicopter ASB No. 204-75-1 for Model 204B
helicopters and ASB No. 205-75-5 for Model 205A-1 helicopters, both
Revision C and both dated April 25, 1979. ASB No. 204-75-1 and ASB No.
205-75-5 specify visually inspecting the M/R blades during each daily in-
spection. ASB No. 204-75-1 and ASB No. 205-75-5 also provide instruc-
tions for repetitively inspecting the blades every 1,000 hours of operation
or every 12 months, whichever occurs first.

AD Requirements

This AD requires within 25 hours time-in-service (TIS) or 2 weeks,
whichever occurs first, and thereafter at intervals not to exceed 25
hours TIS or 2 weeks, whichever occurs first, cleaning the upper and
lower exposed surfaces of each M/R blade from an area starting at the
butt end of the blade to three inches outboard of the doublers. Using a
3X or higher power magnifying glass and a light, this AD also requires
visually inspecting various M/R blade parts for a crack or corrosion.
If there is a crack, corrosion, an edge void, loose or damaged adhesive
squeeze-out, or an edge delamination, before further flight, this AD
requires repairing the M/R blade or replacing it with an airworthy M/R
blade, depending on whether the condition is within maximum repair
damage limits.
This AD also requires reporting information about any cracks found
during the inspection to the FAA within 10 days.

Differences Between This AD and the Service Information

This AD requires all inspections every 25 hours TIS or 2 weeks,
whichever occurs first. ASB 204-75-1 and ASB 205-75-5 call for daily
visual inspections, and inspections, rework, and refinishing every
1,000 hours TIS or 12 months, whichever occurs first. The service
information applies to Bell M/R blade P/N 204-011-250. This AD applies
to HTC M/R blade P/N 204P2100-101.

Interim Action

We consider this AD to be an interim action. The notification of a
crack in the M/R blade that is required by this AD may enable us to
obtain better insight into the cause of the M/R blade cracking. This
information may help us develop additional action to address this
unsafe condition. Once this action is developed, approved, and
available, we might consider additional rulemaking.

Costs of Compliance


We estimate that this AD affects 10 helicopters of U.S. Registry
and that labor costs average $85 per work-hour. Based on these
estimates, we expect the following costs:
Cleaning and performing all inspections of a set of M/R
blades (2 per helicopter) requires 0.5 work-hour for a cost of $43 per
helicopter and $430 for the U.S. fleet per inspection cycle.
Replacing an M/R blade requires 12 work-hours and parts
cost $86,000 for a total cost of $87,020 per blade.
Reporting the inspection results required by this AD will
require about 0.5 work-hour for a cost of $43 per helicopter and $430
for the U.S. fleet per report.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting required by this AD
is mandatory. Comments concerning the accuracy of this burden and
suggestions for reducing the burden should be directed to the FAA at
800 Independence Ave. SW, Washington, DC 20591. ATTN: Information
Collection Clearance Officer, AES-200.

FAA's Justification and Determination of the Effective Date

Providing an opportunity for public comments prior to adopting
these AD requirements would delay implementing the safety actions
needed to correct this known unsafe condition. Therefore, we find that
the risk to the flying public justifies waiving notice and comment
prior to the adoption of this rule because the required corrective
actions must be accomplished within two weeks.
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
prior public comment before issuing this AD are impracticable and that
good cause exists to make this AD effective in less than 30 days.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
Government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):